HyperCFD™ 2.5.1
Supersonic and Hypersonic Rocket Analysis
Determine drag coefficient (Cd), center of pressure (Xcp), CN-alpha and Cm-alpha of supersonic and hypersonic rockets and re-entry vehicles. In addition, on a separate screen HyperCFD displays and plots CN-Body, CN-Fins, CN-Total and Cm-Total as a function of angle of attack (AOA) using up/down controls. HyperCFD uses empirical corrections to the modified Newtonian surface inclination method that allows excellent results from Mach 1.05 to Mach 20. Includes a wide variety of nose cone shapes and fin cross-sections. Nose cone shapes include, conical, elliptical, parabolic, power series Sears-Haack, tangent ogive and spherical segment. Fin cross-sections include single wedge, symmetrical double wedge, arbitrary double wedge, biconvex section, streamline section, round-nose section, and elliptical section fin shapes. HyperCFD is useful to determine supersonic rocket drag and Cp location for level 3 flights. Useful companion program to AeroCFD & 2D-WING™.

New Features
1) Temperature on the surface of the rocket relative to free-stream conditions.
2) Pressure and temperature can be output to a PLT file and read as a text file.
3) Cd estimation as a function of AOA based on Newtonian surface inclination theory.
4) Cd estimation and XCp estimation as a function of small angle of attack (1 to 2 degrees).
5) Cd estimation for decreasing cross-sectional components.

HyperCFD Results
Case #1: Re-Entry Vehicle

HyperCFD main screen displaying re-entry vehicle


HyperCFD re-entry vehicle pressure distribution


Case #2: Conical Nose Cone



Case #3: Missile With Fins

Hypersonic missile In free flight


HyperCFD main screen displaying hypervelocity missile


HyperCFD fin geometry screen for hypervelocity missile


HyperCFD Motor On/Off screen



HyperCFD Biconic Re-Entry Vehicle

HyperCFD analysis of a Biconic re-entry vehicle operating at Mach 5 to determine Cd (drag coefficient), Xcp (center of pressure) and CNa (lift slope)

The following links illustrate how HyperCFD has been used to analyze re-entry vehicles.
Revisiting China’s Early Warhead Designs
Iranian Warhead Evolution


Mars Phoenix Entry Capsule Aerodynamics

Orientation of the Mars Phoenix entry capsule


HyperCFD analysis of the Mars Phoenix entry capsule operating at Mach 18.5 to determine Cd, Xcp and CNa.

SYSTEM REQUIREMENTS
(1) Screen resolution: 800 X 600
(2) System: Windows 98, XP, Vista, Windows 7 (32 bit and 64 bit), NT or Mac with emulation
(3) Processor Speed: Pentium 3 or 4
(4) Memory: 64 MB RAM
(5) English (United States) Language
(6) 256 colors